ES2401520A2 - Manufacturing procedure of a composite part of a closed compartment with an integrated access assembly - Google Patents
Manufacturing procedure of a composite part of a closed compartment with an integrated access assembly Download PDFInfo
- Publication number
- ES2401520A2 ES2401520A2 ES201131291A ES201131291A ES2401520A2 ES 2401520 A2 ES2401520 A2 ES 2401520A2 ES 201131291 A ES201131291 A ES 201131291A ES 201131291 A ES201131291 A ES 201131291A ES 2401520 A2 ES2401520 A2 ES 2401520A2
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- ES
- Spain
- Prior art keywords
- housing panel
- laminates
- fabrics
- lid
- wing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/545—Perforating, cutting or machining during or after moulding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
- Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
- Y10T156/1062—Prior to assembly
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Vehicle Step Arrangements And Article Storage (AREA)
- Laminated Bodies (AREA)
Abstract
Description
Procedimiento de fabricación de una pieza de material compuesto de un compartimento cerrado con una disposición de acceso integrada Manufacturing procedure of a piece of composite material of a closed compartment with an integrated access arrangement
5 La presente invención se refiere a un procedimiento de fabricación de una pieza de material compuesto de un compartimento cerrado con una disposición de acceso integrada y, más en particular, a un procedimiento de fabricación del revestimiento inferior de un ala de aeronave con una disposición de acceso a una entrada de aire en un tanque de compensación situado en la punta del ala. The present invention relates to a method of manufacturing a piece of composite material of a closed compartment with an integrated access arrangement and, more particularly, to a method of manufacturing the lower lining of an aircraft wing with an arrangement of access to an air inlet in a compensation tank located at the tip of the wing.
10 La estructura principal de las superficies sustentadoras de una aeronave está constituida por un borde de ataque, un cajón de torsión, un borde de salida, una raíz de unión y una punta. El cajón de torsión está constituido por varios elementos estructurales: revestimientos superior e inferior rigidizados por larguerillos por un lado, largueros y costillas por otro lado. Los elementos estructurales que forman un cajón de torsión se fabrican, típicamente, por separado y se unen con la ayuda de un utillaje complicado para 10 The main structure of the supporting surfaces of an aircraft consists of a leading edge, a torsion box, a trailing edge, a connecting root and a point. The torsion box consists of several structural elements: upper and lower coverings stiffened by stringers on one side, stringers and ribs on the other side. The structural elements that form a torsion box are typically manufactured separately and joined together with the help of a complicated tooling for
15 alcanzar las tolerancias requeridas que vienen dadas por los requerimientos aerodinámicos, estructurales y de ensamblaje. 15 reach the required tolerances that are given by the aerodynamic, structural and assembly requirements.
En la actualidad y particularmente en la industria aeronáutica se utilizan de forma masiva materiales compuestos de matriz orgánica y fibras continuas, especialmente CFRP (Fibra de Carbono Reforzada con Plástico) en una gran diversidad de elementos estructurales. Por ejemplo, todos los At present and particularly in the aeronautical industry, composite materials of organic matrix and continuous fibers are used in bulk, especially CFRP (Carbon Fiber Reinforced with Plastic) in a wide variety of structural elements. For example, all
20 elementos constituyentes de los cajones de torsión anteriormente citados (costillas, larguerillos, largueros y revestimientos) pueden ser fabricados usando CFRP. 20 constituent elements of the aforementioned torsion drawers (ribs, stringers, stringers and liners) can be manufactured using CFRP.
Los revestimientos que forman parte de los cajones de torsión están reforzados mediante larguerillos longitudinales en sentido de la envergadura que mejoran tanto la resistencia como el comportamiento a pandeo de los revestimientos, teniendo diferentes secciones transversales tales como The linings that are part of the torsion drawers are reinforced by longitudinal stringers in the direction of the wingspan that improve both the resistance and the buckling behavior of the liners, having different cross sections such as
25 secciones transversales con forma de “T”, “I” o “J”. 25 cross sections shaped like "T", "I" or "J".
Los tanques de combustible de las aeronaves suelen estar alojados en el cajón de torsión del ala de la aeronave. Uno de ellos llamado tanque de ventilación o tanque de compensación incluye medios de ventilación a través de un orificio en el revestimiento inferior para permitir que el aire pueda fluir desde la atmósfera hacia los tanques de combustible cuando se vacían y que una mezcla de gases pueda fluir Aircraft fuel tanks are usually housed in the torsion drawer of the aircraft wing. One of them called a ventilation tank or compensation tank includes ventilation means through a hole in the bottom lining to allow air to flow from the atmosphere into the fuel tanks when they are emptied and a mixture of gases can flow
30 desde los tanques hacia la atmósfera cuando se llenan. 30 from the tanks to the atmosphere when they are filled.
El diseño y la fabricación de dichos cajones de torsión implica varios problemas. Uno de ellos es la disposición de acceso a dicho orificio de ventilación. The design and manufacture of such torsion drawers involves several problems. One of them is the access arrangement to said ventilation hole.
En las soluciones conocidas para dicho problema, el revestimiento inferior se fabrica dejando un entrante alrededor del orificio de ventilación para la instalación posterior en él de una disposición de acceso 35 apropiada. Una desventaja importante de esta solución es que requiere una operación de instalación In the known solutions for said problem, the bottom lining is manufactured by leaving a recess around the ventilation hole for subsequent installation therein of an appropriate access arrangement 35. An important disadvantage of this solution is that it requires an installation operation
durante el montaje del cajón de torsión del ala que implica tiempo y costes. during the assembly of the torsion box of the wing that implies time and costs.
Esta invención se centra en la solución de este problema This invention focuses on solving this problem.
Un objeto de la presente invención es proporcionar un procedimiento más eficiente para la An object of the present invention is to provide a more efficient method for the
40 fabricación del revestimiento inferior del ala de una aeronave que incluye una disposición de acceso al orificio de ventilación de un tanque de compensación y piezas similares de material compuesto con una disposición de acceso a compartimentos interiores. 40 manufacturing of the lower lining of the wing of an aircraft that includes an access arrangement to the vent hole of a compensation tank and similar pieces of composite material with an access arrangement to interior compartments.
Estos y otros objetos se consiguen con un procedimiento para la fabricación de una pieza de material compuesto de un compartimento cerrado, teniendo dicha pieza al menos una disposición de 45 acceso a dicho compartimento a través de un orificio en dicha pieza, comprendiendo dicha disposición de acceso una tapa para dicho orificio y un panel de alojamiento de dicha tapa, que comprende los siguientes pasos: a) proporcionar laminados comunes de un material compuesto para dicha tapa y dicho panel de alojamiento en un estado fresco; b) cortar dichos laminados comunes por el perímetro previsto para dicha tapa y separar los laminados de la tapa y los laminados del panel de alojamiento; c) fabricar These and other objects are achieved with a method for manufacturing a piece of composite material of a closed compartment, said piece having at least one arrangement for access to said compartment through a hole in said piece, said access arrangement comprising a lid for said hole and a housing panel of said lid, comprising the following steps: a) providing common laminates of a composite material for said lid and said housing panel in a fresh state; b) cutting said common laminates by the perimeter provided for said lid and separating the laminates from the lid and the laminates from the housing panel; c) manufacture
50 separadamente, por un lado, la tapa usando dichos laminados de la tapa y, por otro lado, la pieza junto con el panel de alojamiento usando dichos laminados del panel de alojamiento. 50 separately, on the one hand, the lid using said laminates of the lid and, on the other hand, the part together with the housing panel using said laminates of the housing panel.
En realizaciones de la invención, la fabricación de la pieza junto con dicho panel de alojamiento comprende pasos de: c1) colocar un laminado extendido del panel de alojamiento formado por dichos In embodiments of the invention, the manufacturing of the part together with said housing panel comprises steps of: c1) placing an extended laminate of the housing panel formed by said
laminados del panel de alojamiento y telas adicionales apiladas entre ellos sobre un molde apropiado para dicha pieza en la posición prevista para dicha disposición de acceso; c2) colocar un muerto en el espacio interior de dicho laminado extendido del panel de alojamiento; c3) apilar telas de un material compuesto sobre dicho laminado extendido del panel de alojamiento y sobre dicho muerto para conformar dicha pieza junto con dicho panel de alojamiento; c4) curar el conjunto; c5) retirar el muerto. Se consigue con ello un procedimiento para la fabricación de dicha pieza junto con el panel de alojamiento debidamente configurada para su ensamblaje con la tapa. laminates of the housing panel and additional fabrics stacked between them on a mold suitable for said piece in the position provided for said access arrangement; c2) placing a dead person in the interior space of said extended laminate of the housing panel; c3) stacking fabrics of a composite material on said extended laminate of the housing panel and on said dead to form said piece together with said housing panel; c4) cure the whole; c5) remove the dead. This achieves a process for manufacturing said part together with the housing panel properly configured for assembly with the lid.
En realizaciones de la invención dicha pieza es el revestimiento inferior de un ala de aeronave, dicho compartimento cerrado es un tanque de compensación colocado en la punta del ala y dicho orificio es un orificio de entrada de aire. Se logra con ello un procedimiento para la fabricación de un revestimiento inferior de un ala de aeronave (con, preferentemente, CFRP), que incluye la fabricación de la tapa y del panel de alojamiento de la disposición de acceso al tanque de compensación sin desperdiciar ningún material como sucedía en la técnica anterior. In embodiments of the invention said part is the bottom lining of an aircraft wing, said closed compartment is a compensation tank placed at the tip of the wing and said hole is an air inlet hole. This achieves a process for manufacturing a lower lining of an aircraft wing (with, preferably, CFRP), which includes the manufacture of the cover and the housing panel of the compensation tank access arrangement without wasting any material as it happened in the prior art.
En realizaciones de la invención dichos laminados comunes son paquetes de telas de CFRP. Se logra con ello un procedimiento para la fabricación de un revestimiento inferior de un ala de aeronave que incluye la fabricación simultánea de la tapa y el panel de alojamiento de la disposición de acceso al tanque de compensación. In embodiments of the invention said common laminates are packages of CFRP fabrics. This achieves a process for manufacturing a lower lining of an aircraft wing that includes the simultaneous manufacture of the cover and the housing panel of the compensation tank access arrangement.
En realizaciones de la invención dicho laminado extendido del panel de alojamiento se coloca sobre una base previamente dispuesta sobre un molde adecuado para la pieza en la posición prevista para dicha disposición de acceso que comprende una capa adhesiva y una capa metálica. Se logra con ello un procedimiento para la fabricación de un revestimiento inferior de un ala de aeronave que incluye la fabricación simultánea de la tapa y el panel de alojamiento de la disposición de acceso al tanque de compensación y que permite la incorporación de una capa metálica al panel de alojamiento de la disposición de acceso y también a los bordes del revestimiento inferior para la protección contra rayos. In embodiments of the invention said extended laminate of the housing panel is placed on a base previously arranged on a mold suitable for the piece in the position provided for said access arrangement comprising an adhesive layer and a metal layer. This achieves a process for the manufacture of a lower lining of an aircraft wing that includes the simultaneous manufacture of the cover and the housing panel of the compensation tank access arrangement and which allows the incorporation of a metal layer into the housing panel of the access arrangement and also to the edges of the bottom lining for lightning protection.
La invención también comprende un revestimiento inferior de ala de aeronave con una disposición de acceso a una entrada de aire en un tanque de compensación colocado en la punta del ala fabricado con alguno de los procedimientos antes mencionados y a una aeronave que comprende dicho revestimiento inferior. The invention also comprises a lower aircraft wing liner with an access arrangement for an air inlet in a compensation tank placed at the tip of the wing manufactured with any of the aforementioned procedures and to an aircraft comprising said lower liner.
Otras características y ventajas de la presente invención se desprenderán de la descripción detallada que sigue de realizaciones ilustrativas de su objeto en relación con las figuras que se acompañan. Other features and advantages of the present invention will be apparent from the following detailed description of illustrative embodiments of its object in relation to the accompanying figures.
La Figura 1 es una vista esquemática transversal de un revestimiento inferior de un ala de aeronave con una disposición conocida de acceso a la entrada de aire en el tanque de compensación colocado en la punta del ala. Figure 1 is a schematic cross-sectional view of a bottom lining of an aircraft wing with a known arrangement of access to the air inlet in the compensation tank placed at the tip of the wing.
La Figura 2 es una vista en perspectiva del panel de alojamiento utilizado en la disposición de acceso de la Figura 1. Figure 2 is a perspective view of the housing panel used in the access arrangement of Figure 1.
La Figura 3 es una vista esquemática transversal de un revestimiento inferior de un ala de aeronave con una disposición de acceso a la entrada de aire en el tanque de compensación colocado en la punta del ala según la presente invención. Figure 3 is a schematic cross-sectional view of a lower lining of an aircraft wing with an air intake access arrangement in the compensation tank placed at the tip of the wing according to the present invention.
Las Figuras 4 y 5 ilustran los pasos principales de un procedimiento para fabricar los principales componentes de una disposición de acceso en un revestimiento inferior de un ala de aeronave para la entrada de aire en el tanque de compensación colocado en la punta del ala según la presente invención. Figures 4 and 5 illustrate the main steps of a process for manufacturing the main components of an access arrangement in a lower liner of an aircraft wing for the entry of air into the compensation tank placed at the tip of the wing according to the present invention.
La Figura 6 es una vista transversal de la estructura del laminado del revestimiento inferior de un ala de aeronave con una disposición de acceso según la presente invención. Figure 6 is a cross-sectional view of the laminate structure of the lower lining of an aircraft wing with an access arrangement according to the present invention.
La Figura 7 es la misma vista que la Figura 6 incluyendo una base con una capa adhesiva y una capa metálica bajo disposición de acceso. Figure 7 is the same view as Figure 6 including a base with an adhesive layer and a metal layer under access arrangement.
La invención se refiere a disposiciones de acceso a compartimentos cerrados tales como la disposición de acceso ilustrada en las Figuras 1 y 2 a un tanque de ventilación ubicado en un ala de aeronave a través de un orificio de ventilación 11 en su revestimiento inferior 13 realizado con un material compuesto. The invention relates to access arrangements for closed compartments such as the access arrangement illustrated in Figures 1 and 2 to a ventilation tank located in an aircraft wing through a ventilation hole 11 in its lower lining 13 made with a composite material
A los efectos de la presente invención, dicha disposición de acceso según el estado de la técnica comprende un panel de alojamiento 15 y una tapa 17, cada uno de ellos de un material apropiado, que se For the purposes of the present invention, said access arrangement according to the state of the art comprises a housing panel 15 and a cover 17, each of them of an appropriate material, which is
fabrican por separado y se instalan en el revestimiento inferior del ala utilizando medios adecuados de sujeción. They are manufactured separately and installed in the lower lining of the wing using suitable fastening means.
Los objetivos de la presente invención, tal como se ilustra en la Figura 3, son que el panel de alojamiento 25 y la tapa 27 se fabriquen conjuntamente con el revestimiento inferior 13 y que la tapa 27 se fabrique de una manera que asegure una buena adaptación al panel de alojamiento 25. The objectives of the present invention, as illustrated in Figure 3, are that the housing panel 25 and the cover 27 are manufactured together with the lower liner 13 and that the cover 27 is manufactured in a manner that ensures a good fit to housing panel 25.
El procedimiento de fabricación para alcanzar dichos objetivos comprende los siguientes pasos (ver Figuras 4, 5, 6): The manufacturing process to achieve these objectives includes the following steps (see Figures 4, 5, 6):
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- Proporcionar laminados comunes 31, 31’, 31’’ de un material compuesto para la tapa 27 y el panel de alojamiento 25 en un estado fresco. Tienen una longitud diferente para conformar el panel de alojamiento con bordes en rampa como en la Figura 2. Provide common laminates 31, 31 ’, 31’ of composite material for lid 27 and housing panel 25 in a cool state. They have a different length to form the housing panel with ramp edges as in Figure 2.
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- Cortar dichos laminados comunes 31, 31’, 31’’ por el perímetro previsto para la tapa 27 y obtener, por un lado, los laminados de la tapa 33, 33’, 33’’ y, por otro lado, los laminados del panel de alojamiento 35, 35’, 35’’. El estado no curado de los laminado facilita la operación de corte utilizando una herramienta de corte convencional. Cut said common laminates 31, 31 ', 31' 'by the perimeter provided for the lid 27 and obtain, on the one hand, the laminates of the lid 33, 33', 33 '' and, on the other hand, the laminates of the panel of housing 35, 35 ', 35' '. The uncured state of the laminates facilitates the cutting operation using a conventional cutting tool.
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- Los laminados de la tapa 33, 33’, 33’ se usan para obtener la tapa 27 colocándolos sobre un molde apropiado y sometiendo el conjunto a un proceso de curado. The laminates of the lid 33, 33 ', 33' are used to obtain the lid 27 by placing them on an appropriate mold and subjecting the assembly to a curing process.
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- Los laminados del panel de alojamiento 35, 35’, 35’’ se usan junto con telas adicionales 37, 37’ a ser apiladas entre ellos para preparar y colocar un laminado extendido del panel de alojamiento 39 sobre el molde 19 a utilizar para la fabricación del revestimiento inferior 13 en la posición prevista para dicha disposición de acceso. Dichas telas adicionales 37, 37’ se usan para dar al laminado extendido del panel de alojamiento 39 un espesor mayor que el de la tapa 27 para proporcionar espacio para su instalación de manera que se mantenga la continuidad aerodinámica de la superficie exterior de la disposición de acceso. The laminates of the housing panel 35, 35 ', 35' 'are used together with additional fabrics 37, 37' to be stacked between them to prepare and place an extended laminate of the housing panel 39 on the mold 19 to be used for manufacturing of the lower lining 13 in the position provided for said access arrangement. Said additional fabrics 37, 37 'are used to give the extended laminate of the housing panel 39 a thickness greater than that of the cover 27 to provide space for its installation so as to maintain the aerodynamic continuity of the outer surface of the arrangement of access.
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- Apilar telas 23 de material compuesto sobre dicho laminado extendido del panel de alojamiento 39 y sobre un muerto 29 dispuesto en su espacio interior para conformar el revestimiento inferior 13. Este paso puede realizarse mediante técnicas convencionales y, en particular, apilando telas de "prepeg" de CFRP utilizando una máquina ATL (hay que señalar a este respecto que la Figura 6 no muestra las rampas de las telas 23 a escala real). Stack composite fabrics 23 on said extended laminate of the housing panel 39 and on a dead 29 disposed in its interior space to form the bottom liner 13. This step can be carried out by conventional techniques and, in particular, by stacking "prepeg" fabrics of CFRP using an ATL machine (it should be noted in this regard that Figure 6 does not show the ramps of the fabrics 23 at full scale).
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- Por último, el conjunto se cura y después de ello se extrae el muerto 29 del conjunto curado. Preferiblemente el muerto 29 está hecho de invar para controlar la geometría interior de la disposición de acceso del revestimiento inferior para asegurar un buen ensamblaje de la tapa 27. Finally, the set is cured and after that the dead 29 is removed from the cured set. Preferably the dead 29 is made of invar to control the interior geometry of the access arrangement of the lower liner to ensure a good assembly of the cover 27.
En realizaciones de la invención, dichos laminados comunes 31, 31’, 31’’, cuya estructura debe cumplir con los requisitos de resistencia de la tapa 27, son paquetes de telas de CFRP. In embodiments of the invention, said common laminates 31, 31 ’, 31’, whose structure must meet the strength requirements of the cover 27, are fabric packages of CFRP.
En realizaciones de la invención (ver Figura 7) dicho laminado extendido del panel de alojamiento 39 se coloca sobre una base previamente colocada sobre el molde 19 que comprende: In embodiments of the invention (see Figure 7) said extended laminate of the housing panel 39 is placed on a base previously placed on the mold 19 comprising:
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- Una capa adhesiva 41; An adhesive layer 41;
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- Una capa metálica 43 (preferiblemente una malla de bronce). A metallic layer 43 (preferably a bronze mesh).
Aunque la presente invención se ha descrito enteramente en conexión con realizaciones preferidas, es evidente que se pueden introducir aquellas modificaciones dentro de su alcance, no considerando éste como limitado por las anteriores realizaciones, sino por el contenido de las reivindicaciones siguientes. Although the present invention has been described entirely in connection with preferred embodiments, it is evident that those modifications can be made within its scope, not considering this as limited by the above embodiments, but by the content of the following claims.
Claims (10)
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ES201131291A ES2401520B1 (en) | 2011-07-28 | 2011-07-28 | MANUFACTURING PROCEDURE OF A COMPOSITE MATERIAL PART OF A CLOSED COMPARTMENT WITH AN INTEGRATED ACCESS PROVISION |
| US13/348,170 US9073271B2 (en) | 2011-07-28 | 2012-01-11 | Manufacturing procedure of a composite part of a closed compartment with an integrated access assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ES201131291A ES2401520B1 (en) | 2011-07-28 | 2011-07-28 | MANUFACTURING PROCEDURE OF A COMPOSITE MATERIAL PART OF A CLOSED COMPARTMENT WITH AN INTEGRATED ACCESS PROVISION |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| ES2401520A2 true ES2401520A2 (en) | 2013-04-22 |
| ES2401520R1 ES2401520R1 (en) | 2013-08-05 |
| ES2401520B1 ES2401520B1 (en) | 2014-06-10 |
Family
ID=47596433
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| ES201131291A Active ES2401520B1 (en) | 2011-07-28 | 2011-07-28 | MANUFACTURING PROCEDURE OF A COMPOSITE MATERIAL PART OF A CLOSED COMPARTMENT WITH AN INTEGRATED ACCESS PROVISION |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US9073271B2 (en) |
| ES (1) | ES2401520B1 (en) |
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| WO2001058680A1 (en) * | 2000-02-11 | 2001-08-16 | Bae Systems Plc | A method of reinforcing a laminated member such as a skin for an aircraft |
| ES2240831T3 (en) * | 2001-07-21 | 2005-10-16 | Bae Systems Plc | AIRCRAFT STRUCTURAL COMPONENTS. |
| WO2010004159A2 (en) * | 2008-06-26 | 2010-01-14 | Airbus Operations | Reinforced aircraft fuselage panel and method of manufacture. |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5516041B2 (en) * | 1973-10-03 | 1980-04-28 | ||
| FR2756211B1 (en) * | 1996-11-26 | 1999-01-29 | Eurocopter France | PROCESS FOR PRODUCING A FLEXIBLE AND TORSIBLE COMPOSITE ELEMENT |
| US20030146346A1 (en) * | 2002-12-09 | 2003-08-07 | Chapman Jr W. Cullen | Tubular members integrated to form a structure |
| GB0623328D0 (en) * | 2006-11-22 | 2007-01-03 | Airbus Uk Ltd | A method for forming a feature in a piece of composite material |
| US7934676B2 (en) * | 2007-06-28 | 2011-05-03 | The Boeing Company | Pre-fabricated article for EME protection of an aircraft |
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2011
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2012
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| US5452867A (en) * | 1992-10-09 | 1995-09-26 | Deutsche Aerospace Airbus Gmbh | Shell structural component made of fiber composite material |
| WO2001058680A1 (en) * | 2000-02-11 | 2001-08-16 | Bae Systems Plc | A method of reinforcing a laminated member such as a skin for an aircraft |
| ES2240831T3 (en) * | 2001-07-21 | 2005-10-16 | Bae Systems Plc | AIRCRAFT STRUCTURAL COMPONENTS. |
| WO2010004159A2 (en) * | 2008-06-26 | 2010-01-14 | Airbus Operations | Reinforced aircraft fuselage panel and method of manufacture. |
Also Published As
| Publication number | Publication date |
|---|---|
| US9073271B2 (en) | 2015-07-07 |
| US20130026294A1 (en) | 2013-01-31 |
| ES2401520B1 (en) | 2014-06-10 |
| ES2401520R1 (en) | 2013-08-05 |
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